Wing for an aircraft

ABSTRACT

An aircraft wing, including a main wing, a leading edge high lift assembly including a high lift body, and an assembly connecting the high lift body to the main wing. The high lift body is movable relative to the main wing between stowed and deployed positions. The connection assembly includes at least one rotation element mounted to the high lift body and rotatably mounted to the main wing. The main wing comprises an upper panel with a leading edge portion and a lower skin panel. The high lift body has a leading and a trailing edge. The high lift body trailing edge moves along the main wing upper skin panel leading edge portion when the high lift body is moved between the stowed and deployed positions. The upper skin panel leading edge portion is elastically deformed when the high lift body is moved from the stowed to the deployed position.

CROSS-REFERENCES TO RELATED APPLICATIONS

This application claims the benefit of the German patent application No.102021107277.8 filed on Mar. 23, 2021, the entire disclosures of whichare incorporated herein by way of reference.

FIELD OF THE INVENTION

The present invention relates to a wing for an aircraft. Further aspectsof the invention relate to a leading edge high lift assembly for such awing as well as an aircraft comprising such a leading edge high liftassembly and/or such a wing.

BACKGROUND OF THE INVENTION

The wing comprises a main wing and a leading edge high lift assemblymovable relative to the main wing to increase lift of the wing. Theleading edge high lift assembly comprises a high lift body and aconnection assembly. The high lift body is preferably a droop high liftbody referred to as droop nose, droop leading edge, droop flap or slat,in particular sealed slat. The connection assembly is configured forconnecting the high lift body to the main wing, in particular to theleading edge of the main wing, in such a way that the high lift body ismovable relative to the main wing between a stowed position and adeployed position. The stowed position relates to a position where thewing profile has a lower curvature and might also be referred to asstraight position, normal position, cruise position or retractedposition, while the deployed position relates to a position where thewing profile has a higher curvature and might also be referred to asdrooped position, landing position or extended position.

The connection assembly comprises at least one rotation element, such asa rotation rod or a part of the high lift body structure, that ismounted to the high lift body and that is mounted to the main wingrotatably about an axis of rotation. The rotation element is mounted tothe high lift body directly or indirectly and in a fixed or rotatablemanner, preferably in a fixed, non-rotatable manner, e.g., by a hingebetween the end of the rotation element and the high lift body andadditionally by a fixing link that is hinged to the rotation element andthat is hinged to the high lift body spaced apart from the rotationelement, so that a relative rotation of the high lift body and therotation element is prevented. The axis of rotation is preferablyarranged at a lower part of the main wing near or at a lower skin andpreferably extends in parallel to the span direction and/or in parallelto the extension of leading edge along the wing, so that the high liftbody is preferably rotated about the axis of rotation when moved betweenthe stowed position and the deployed position.

The main wing comprises an upper skin panel for contact with an ambientflow on an upper side of the main wing, and a lower skin panel forcontact with an ambient flow on a lower side of the main wing. The upperskin panel has a leading edge portion in the area of a leading edge ofthe main wing and facing the high lift body. The upper skin panel andthe lower skin panel might be joined at the leading edge of the mainwing, or might have an open end at the leading edge of the main wing,where they might be connected or supported against each other via afront spar.

The high lift body extends between a leading edge and a trailing edge,the trailing edge preferably in parallel to the axis of rotation. Thetrailing edge of the high lift body is configured to move, preferablyslide, along the outer surface of the leading edge portion of the upperskin panel of the main wing, preferably in contact with the outersurface of the leading edge portion of the upper skin panel, when thehigh lift body is moved between the stowed position and the deployedposition. The contact might generally seal the high lift body to theupper skin panel for essential flow, but it might also be formed suchthat a leakage flow is permitted. It is also possible that the trailingedge of the high lift body moves along the outer surface of the leadingedge portion of the upper skin panel of the main wing out of contactwith the outer surface of the leading edge portion of the upper skinpanel, when the high lift body is moved between the stowed position andthe deployed position, so that a defined gap is formed between thetrailing edge of the high lift body and the outer surface of the leadingedge portion of the upper skin panel during movement of the high liftbody, thereby allowing a defined leakage flow or even essential flowthrough the gap.

Similar wings are known in the art. By increasing the curvature of thewing profile when the high lift body is moved to the deployed position,lift of the related aircraft can be increased, in particular to allowapproach and landing with lower speed and on shorter runways. High liftassemblies with a drooping, downward rotating high lift body that issealed to the leading edge portion of the upper skin panel, such asdroop nose assemblies, related to simple and effective high liftdevices. However, some known devices cause a pressure peak in the areaof the transition between the trailing edge of the high lift body andthe leading edge portion of the upper skin panel.

SUMMARY OF THE INVENTION

Therefore, an object of the present invention is to provide a wingcausing a smooth pressure profile along its upper skin panel.

This object is achieved in that the leading edge portion of the upperskin panel is configured to be elastically deformed, in particular benttowards the lower skin panel, when the high lift body is moved from thestowed position to the deployed position. In such a way, a smoothtransition from the trailing edge of the high lift body to the upperskin panel can be achieved avoiding small and discontinuous curvatureradii. This results in a smooth pressure profile along the upper skinpanel without undesired pressure peaks.

According to a preferred embodiment, the leading edge portion of theupper skin panel is configured to be elastically deformed, when the highlift body is moved from the stowed position to the deployed position, byat least one link element that is mounted, preferably rotatably mounted,preferably at one end, to the rotation element and that is, preferablyat the other end, mounted to, preferably rotatably mounted to, theleading edge portion of the upper skin panel. When the rotation elementrotates downwards to move the high lift body into the deployed position,the link element mounted to the rotation element pulls the leading edgeportion of the upper skin panel downwards, too. When the rotationelement rotates upwards to move the high lift body back into the stowedposition, the link element pushes the leading edge portion of the upperskin panel back upwards into the undeformed state. By such a linkelement the curvature of the leading edge portion of the upper skinpanel can be precisely adapted to form the desired pressure profile.

Additionally or alternatively, it is preferred that the leading edgeportion of the upper skin panel is configured to be elasticallydeformed, when the high lift body is moved from the stowed position tothe deployed position, by at least one rope element that is attached,preferably at one end, to the rotation element and that is, preferablyat the other end, attached to the leading edge portion of the upper skinpanel. When the rotation element rotates downwards to move the high liftbody into the deployed position, the rope element attached to therotation element pulls the leading edge portion of the upper skin paneldownwards, too. When the rotation element rotates upwards to move thehigh lift body back into the stowed position, the elastic properties ofthe upper skin panel move the leading edge portion of the upper skinpanel back upwards into the undeformed state. By such a rope element thecurvature of the leading edge portion of the upper skin panel can beprecisely adapted to form the desired pressure profile.

Additionally or alternatively, it is preferred that the leading edgeportion of the upper skin panel is configured to be elastically deformedby the trailing edge of the high lift body moving along and contacting,preferably sliding over and continuously contacting, preferably pressingonto, an outer surface of the leading edge portion of the upper skinpanel, when the high lift body is moved from the stowed position to thedeployed position. When the rotation element rotates downwards to movethe high lift body into the deployed position, the trailing edge of thehigh lift body mounted in a fixed or defined position relative to therotation element pushes the leading edge portion of the upper skin paneldownwards, too. When the rotation element rotates upwards to move thehigh lift body back into the stowed position, the elastic properties ofthe upper skin panel move the leading edge portion of the upper skinpanel back upwards into the undeformed state. The trailing edge of thehigh lift body preferably has a defined stiffness to achieve the desireddeformation of the leading edge portion of the upper skin panel. By thetrailing edge of the high lift body deforming the leading edge portionof the upper skin panel the curvature of the leading edge portion of theupper skin panel can be precisely adapted to form the desired pressureprofile in a very simple manner.

According to a preferred embodiment, the wing comprises a rotatingactuator for driving the rotation element about the axis of rotation.Such a rotating actuator is a simple and effective way to drive the highlift body.

In particular, it is preferred that the rotary actuator is mounted,preferably fixedly mounted, to the main wing and has a rotating drivearm linked to the rotation element by a drive link that is, preferablyat one end, rotatably mounted to the drive arm and that is, preferablyat the other end, rotatably mounted to the rotation element. Thisresults in a simple and effective actuator.

Alternatively, it is preferred that the rotary actuator comprises afirst rotating arm and a second rotating arm rotating in oppositedirections about a common axis. The first rotating arm is rotatablymounted to the main wing, and the second rotating arm is rotatablymounted to the rotation element or to the high lift body. In such a way,the common axis is displaced when the actuator is actuated. This resultsin a simple and effective actuator.

According to a preferred embodiment, at least one stiffener is providedat the leading edge portion of the upper skin panel. The stiffenerextends in a span direction, preferably in parallel to the axis ofrotation and/or in parallel to the trailing edge of the high lift body.By such a spanwise stiffener deflection of the leading edge portion ofthe upper skin panel in the span direction can be reduced, in particularbetween different rotation elements or different connection assembliesin the span direction, if present.

In particular, it is preferred that the stiffener is formed separatelyfrom the upper skin panel and is attached to an inner surface of theleading edge portion of the upper skin panel. Preferably, the stiffenerhas an angled profile including a flange element resting against theinner surface of the leading edge portion of the upper skin panel, and aweb element extending angled to the flange element and away from theinner surface of the leading edge portion of the upper skin panel. Suchan angled profile might be an L-, C-, T-, Z-, or I-profile. Such astiffener is lightweight, simple to install, and provides an effectivestiffening.

Alternatively, it is preferred that the stiffener is formed integralwith the leading edge portion of the upper skin panel. For example, thestiffener might be formed by bending a part of the leading edge portionof the upper skin panel made of a metal material, or might be molded aspart of the leading edge portion of the upper skin panel made of a fiberreinforced plastic material. Such an integral stiffener provides asimple form and requires no extra parts.

It is also preferred that the link element and/or the rope element isattached to the leading edge portion of the upper skin panel via thestiffener or in the area of the stiffener. By the attachment to thestiffener with a defined stiffness a defined contact or gap between thetrailing edge of the high lift body and the outer surface of the leadingedge portion of the upper skin panel can be precisely adjusted asdesired. Alternatively, the link element might also be attached to thelink element and/or the rope element in a position spaced from theattachment or from the area of the stiffener.

It is further preferred that the extension of the stiffener normal tothe leading edge portion of the upper skin panel varies in the spandirection. In such a way, the stiffness of the stiffener can be adaptedas required in the span direction.

In particular, it is preferred that the extension of the stiffenernormal to the leading edge portion of the upper skin panel varies in thespan direction in such a way that a maximum extension is in the area ofthe attachment of the link element and/or the rope element, while theextension is decreasing, preferably linearly decreasing, in the spandirection with increasing distance from the area of the attachment ofthe link element and/or the rope element. Likewise, a minimum extensionis located between, preferably centrally between, the link elements orrope elements of each two spanwise neighboring connection assemblies orrotation elements. In such a way, the stiffness of the stiffeners isdistributed in the span direction such that the highest stiffness ispresent in the attachment area of the link element or rope element.

According to a further preferred embodiment, the leading edge portion ofthe upper skin panel has a thickness varying in a chord direction, toadapt the curvature of the leading edge portion of the upper skin panelwhen in the deformed state. In such a way, the thickness of the leadingedge portion of the upper skin panel can be used to tailor the curvatureof the upper skin panel in the deformed state, i.e., when the high liftbody is in the deployed position. Preferably, the thickness of theleading edge portion of the upper skin panel varies analogue to thebending moment resulting from elastic deformation of the leading edgeportion of the upper skin panel, preferably in such a way that thevarying bending stiffness along the chord direction of the leading edgeportion of the upper skin panel, resulting from the varying thickness,compensates the bending moment.

In particular, it is preferred that the thickness of the leading edgeportion of the upper skin panel increases linearly or essentiallylinearly in the chord direction downstream, preferably from the leadingedge downstream. In such a way, the bending stiffness of the leadingedge portion of the upper skin panel in the chord direction can beadapted to compensate the bending moment resulting from elasticdeformation of the leading edge portion of the upper skin panel.

Additionally or alternatively, it is preferred that the leading edgeportion of the upper skin panel is made of a fiber reinforced plastichaving a varying laminate lay-up in the chord direction, to adapt thecurvature of the leading edge portion of the upper skin panel when inthe deformed state. In such a way, the laminate lay-up of the leadingedge portion of the upper skin panel can be used to tailor the curvatureof the upper skin panel in the deformed state, i.e., when the high liftbody is in the deployed position. Preferably, the laminate lay-up of theleading edge portion of the upper skin panel varies analogue to thebending moment resulting from elastic deformation of the leading edgeportion of the upper skin panel, preferably in such a way that thevarying bending stiffness along the chord direction of the leading edgeportion of the upper skin panel, resulting from the varying laminatelay-up, compensates the bending moment. Preferably, the laminate lay-upof the leading edge portion of the upper skin panel increases linearlyin the chord direction downstream, preferably from the leading edgedownstream.

Additionally or alternatively, it is preferred that the leading edgeportion of the upper skin panel is provided with at least onereinforcement element, preferably attached to the inner surface of theupper skin panel, extending in the chord direction to vary the bendingstiffness of the leading edge portion of the upper skin panel along thechord direction, to adapt the curvature of the leading edge portion ofthe upper skin panel when in the deformed state. The reinforcementelement might itself have a bending stiffness constant or varying in thechord direction. In such a way, the reinforcement element can be used totailor the curvature of the upper skin panel in the deformed state,i.e., when the high lift body is in the deployed position. Preferably,the reinforcement element is configured such that the bending stiffnessof the leading edge portion of the upper skin panel varies in the chorddirection analogue to the bending moment resulting from elasticdeformation of the leading edge portion of the upper skin panel, inorder to compensate the bending moment. Preferably, the reinforcementelement is configured such that the bending stiffness of the leadingedge portion of the upper skin panel increases linearly in the chorddirection downstream, preferably from the leading edge downstream.

According to a further preferred embodiment, the leading edge high liftassembly comprises a further connection assembly spaced from theconnection assembly in the span direction and preferably formed as theconnection assembly. Preferably at least two spaced connectionassemblies are provided to carry each high lift body. Each connectionassembly might also comprise more than one rotation element. In such away, a stable hold and movement of the high lift body is achieved.

A further aspect of the invention relates to a leading edge high liftassembly for the wing according to any of the afore-describedembodiments. The leading edge high lift assembly comprises a high liftbody and a connection assembly for connecting the high lift body to amain wing in such a way that the high lift body is movable relative tothe main wing between a stowed position and a deployed position. Theconnection assembly comprises a rotation element that is mounted to thehigh lift body and that is configured to be mounted to the main wingrotatably about an axis of rotation. The high lift body extends betweena leading edge and a trailing edge, wherein in an installed state thetrailing edge of the high lift body is configured to move along theleading edge portion of an upper skin panel of the main wing, when thehigh lift body is moved between the stowed position and the deployedposition. The leading edge high lift assembly is configured such that inan installed state the leading edge portion of the upper skin panel canbe elastically deformed, when the high lift body is moved from thestowed position to the deployed position Features and effects describedabove in connection with the wing apply vis-a-vis also to the leadingedge high lift assembly.

A further aspect of the invention relates to an aircraft comprising thewing according to any of the afore-described embodiments and/orcomprising the leading edge high lift assembly according to any of theafore described embodiments. Features and effects described above inconnection with the wing and in connection with the leading edge highlift assembly apply vis-a-vis also to the aircraft.

BRIEF DESCRIPTION OF THE DRAWINGS

Preferred embodiments of the present invention are explained hereinafterin more detail by means of a drawing.

FIG. 1 shows a perspective view of an aircraft according to theinvention,

FIG. 2 shows a schematic cross-sectional view across the span directionof a wing according to a first embodiment of the invention,

FIGS. 3a and 3b show a schematic cross-sectional view across the spandirection of a wing according to a second embodiment of the invention,

FIG. 4 shows a schematic cross-sectional view across the span directionof a wing according to a third embodiment of the invention,

FIG. 5 shows a schematic cross-sectional view of across the spandirection a wing according to a fourth embodiment of the invention,

FIG. 6 shows a schematic cross-sectional view across the span directionof a wing according to a fifth embodiment of the invention,

FIG. 7 shows a schematic cross-sectional view across the span directionof a wing according to a sixth embodiment of the invention,

FIG. 8 shows a schematic cross-sectional view across the chord directionof the wing shown in FIG. 7, and

FIG. 9 shows a schematic cross-sectional view across the span directionof a wing according to a seventh embodiment of the invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

In FIG. 1, an embodiment of an aircraft 1 according to the presentinvention is illustrated. The aircraft 1 comprises a fuselage 3, wings5, a vertical tail plane 7 and a horizontal tail plane 9. FIGS. 2 to 9show in more detail several embodiments of the wings 5.

FIG. 2 shows a first embodiment of the wing 5 according to theinvention. The wing 5 comprises a main wing 11 and a leading edge highlift assembly 13 movable relative to the main wing 11 to increase liftof the wing 5. The leading edge high lift assembly 13 comprises a highlift body 15 and a connection assembly 17. The high lift body 15 is adroop high lift body, also referred to as droop nose, droop leadingedge, droop flap or slat, in particular, a sealed slat. The connectionassembly 17 is configured for connecting the high lift body 15 to theleading edge of the main wing 11 in such a way that the high lift body15 is movable relative to the main wing 11 between a stowed position anda deployed position. The stowed position relates to a position where thewing profile has a lower curvature, while the deployed position relatesto a position where the wing profile has a higher curvature.

The connection assembly 17 comprises at least one rotation element 19that is mounted to the high lift body 15 and that is mounted to the mainwing 11 rotatably about an axis of rotation 21. The rotation element 19is mounted to the high lift body 15 in a fixed, non-rotatable manner bya hinge 25 arranged between the end of the rotation element 19 and thehigh lift body 15, and additionally by a fixing link 27 that is hingedto the rotation element 19 and that is hinged to the high lift body 15spaced apart from the rotation element 19, so that a relative rotationof the high lift body 15 and the rotation element 19 is prevented. Theaxis of rotation 21 is arranged at a lower part of the main wing 11 nearor at a lower skin and preferably extends in parallel to a spandirection 29 and in parallel to the extension of leading edge along thewing 5, so that the high lift body 15 is rotated about the axis ofrotation 21 when moved between the stowed position and the deployedposition.

The main wing 11 comprises an upper skin panel 31 for contact with anambient flow on an upper side of the main wing 11, and a lower skinpanel 33 for contact with an ambient flow on a lower side of the mainwing 11. The upper skin panel 31 has a leading edge portion 35 in thearea of a leading edge of the main wing 11 and facing the high lift body15. The upper skin panel 31 and the lower skin panel 33 have an open end37 at the leading edge of the main wing 11, where they are connected orsupported against each other via a front spar 39.

The high lift body 15 extends between a leading edge 41 and a trailingedge 43, the trailing edge 43 being parallel to the axis of rotation 21.The trailing edge 43 of the high lift body 15 moves in a sliding manneralong the outer surface of the leading edge portion 35 of the upper skinpanel 31 of the main wing 11 in contact with the outer surface of theleading edge portion 35 of the upper skin panel 31, when the high liftbody 15 is moved between the stowed position and the deployed position.The contact generally seals the high lift body 15 to the upper skinpanel 31 for essential flow, but a certain leakage flow might bepermitted.

The leading edge portion 35 of the upper skin panel 31 is configured tobe elastically deformed in such a way that it is bent towards the lowerskin panel 33, when the high lift body 15 is moved from the stowedposition to the deployed position. The elastic deformation can be donein different ways according to the invention, as described hereinafter.

In the embodiment shown in FIG. 2, the leading edge portion 35 of theupper skin panel 31 is configured to be elastically deformed, when thehigh lift body 15 is moved from the stowed position to the deployedposition, by a link element 45 that is rotatably mounted at one end tothe rotation element 19 and that is at the other end rotatably mountedto the leading edge portion 35 of the upper skin panel 31. When therotation element 19 rotates downwards to move the high lift body 15 intothe deployed position, the link element 45 mounted to the rotationelement 19 pulls the leading edge portion 35 of the upper skin panel 31downwards, too. When the rotation element 19 rotates upwards to move thehigh lift body 15 back into the stowed position, the link element 45pushes the leading edge portion 35 of the upper skin panel 31 backupwards into the undeformed state. As an alternative to the link element45, a rope element (not shown) can be used to deform the leading edgeportion 35 of the upper skin element 31. Additional to the deformationcaused by the link element 45, in the embodiment of FIG. 2 the leadingedge portion 35 of the upper skin panel 31 is configured to beelastically deformed by the trailing edge 43 of the high lift body 15moving along in a sliding manner and continuously contacting andpressing onto an outer surface of the leading edge portion 35 of theupper skin panel 31, when the high lift body 15 is moved from the stowedposition to the deployed position. When the rotation element 19 rotatesdownwards to move the high lift body 15 into the deployed position, thetrailing edge 43 of the high lift body 15 mounted in a fixed or definedposition relative to the rotation element 19 pushes the leading edgeportion 35 of the upper skin panel 31 downwards, too. When the rotationelement 19 rotates upwards to move the high lift body 15 back into thestowed position, the elastic properties of the upper skin panel 31assist to move the leading edge portion 35 of the upper skin panel 31back upwards into the undeformed state. In such a way, by the linkelement 45 together with the trailing edge 43 of the high lift body 15the curvature of the leading edge portion 35 of the upper skin panel 31can be precisely adapted to form the desired pressure profile.

The embodiments shown in FIGS. 3 and 4 differ from the embodiment shownin FIG. 2 by the wing 5 comprising a rotating actuator 47 for drivingthe rotation element 19 about the axis of rotation 21. In the embodimentshown in FIG. 3, the rotary actuator 47 is fixedly mounted to the mainwing 11 and has a rotating drive arm 49 linked to the rotation element19 by a drive link 51 that is at one end rotatably mounted to the drivearm 49 and that is at the other end rotatably mounted to the rotationelement 19. FIG. 3a shows the high lift body 15 in the stowed position,while FIG. 3b shows the high lift body 15 in the deployed position.

In the alternative embodiment shown in FIG. 4, the rotary actuator 47comprises a first rotating arm 53 and a second rotating arm 55 rotatingin opposite directions about a common axis 57. The first rotating aim 53is rotatably mounted to the main wing 11, and the second rotating arm 55is rotatably mounted to the rotation element 19 or to the high lift body15, so that the common axis 57 is displaced when the actuator 47 isactuated.

The embodiments shown in FIGS. 5 to 7 differ from the embodiment shownin FIG. 2 by a stiffener 59 being provided at the leading edge portion35 of the upper skin panel 31. The stiffener 59 extends in a spandirection 29 in parallel to the axis of rotation 21 and in parallel tothe trailing edge 43 of the high lift body 15.

In the embodiments shown in FIGS. 5 and 7, the stiffener 59 is formedseparately from the upper skin panel 31 and is attached to an innersurface of the leading edge portion 35 of the upper skin panel 31. Thestiffener 59 has an angled profile including a flange element 61 restingagainst the inner surface of the leading edge portion 35 of the upperskin panel 31, and a web element 63 extending angled to the flangeelement 61 and away from the inner surface of the leading edge portion35 of the upper skin panel 31. The angle profile in the presentembodiment is an L-profile.

In the alternative embodiment shown in FIG. 6, the stiffener 59 isformed integral with the leading edge portion 35 of the upper skin panel31. In case of the upper skin panel 31 being made of a metal materialthe stiffener 59 is formed by bending a part of the leading edge portion35 of the upper skin panel 31. In case of the upper skin panel 31 beingmade of a fiber reinforced plastic material, the stiffener 59 is moldedas part of the leading edge portion 35 of the upper skin panel 31.

In the embodiment shown in FIG. 7, the link element 45 is attached tothe leading edge portion 35 of the upper skin panel 31 via the stiffener59. As shown in FIG. 8, the extension of the stiffener 59 normal to theleading edge portion 35 of the upper skin panel 31 varies in the spandirection 29 in such a way that a maximum extension is in the area ofthe attachment of the link element 45, while the extension is linearlydecreasing in the span direction 29 with increasing distance from thearea of the attachment of the link element 45. Likewise, a minimumextension is located centrally between the link elements 45 of each twospanwise neighboring connection assemblies 17.

The embodiment shown in FIG. 9 differs from the embodiment shown in FIG.2 by the leading edge portion 35 of the upper skin panel 31 having athickness varying in a chord direction 67, to adjust the curvature ofthe leading edge portion 35 of the upper skin panel 31 when in thedeformed state. This allows the thickness of the leading edge portion 35of the upper skin panel 31 to be used to tailor the curvature of theupper skin panel 31 in the deformed state, i.e., when the high lift body15 is in the deployed position. The thickness of the leading edgeportion 35 of the upper skin panel 31 varies analogue to the bendingmoment resulting from elastic deformation of the leading edge portion 35of the upper skin panel 31, in such a way that the varying bendingstiffness along the chord direction 67 of the leading edge portion 35 ofthe upper skin panel 31, resulting from the varying thickness,compensates the bending moment. This means in the present embodiment,the thickness of the leading edge portion 35 of the upper skin panel 31increases linearly or essentially linearly in the chord direction 67downstream, so that a maximum thickness is reached at the downstream end69 of the leading edge portion 35 of the upper skin panel 31.

In case that the leading edge portion 35 of the upper skin panel 31being made of a fiber reinforced plastic, the linear thickness increaseof the upper skin panel 31 might be implemented or assisted by theleading edge portion 35 of the upper skin panel 31 having a linearlyincreasing, e.g., ply-ramped, laminate lay-up (not shown) in the chorddirection 67. Also, one or more reinforcement elements (not shown)attached to the leading edge portion 35 of the upper skin panel 31 mightbe used to implement or assist an increasing bending stiffness of theleading edge portion 35 of the upper skin panel 31 in the chorddirection to compensate an increasing bending moment.

As shown in FIG. 1, the leading edge high lift assembly 13 comprises afurther connection assembly 17′ spaced from the connection assembly 17in the span direction 29 and preferably formed as the connectionassembly 17. At least two spaced connection assemblies 17, 17′ areprovided to carry each high lift body 15. Each connection assembly 17,17′ might also comprise more than one rotation element 19.

By the invention as described above, a smooth transition from thetrailing edge 43 of the high lift body 15 to the upper skin panel 31 canbe achieved avoiding small and discontinuous curvature radii. Thisresults in a smooth pressure profile along the upper skin panel 31without undesired pressure peaks. While at least one exemplaryembodiment of the present invention(s) is disclosed herein, it should beunderstood that modifications, substitutions and alternatives may beapparent to one of ordinary skill in the art and can be made withoutdeparting from the scope of this disclosure. This disclosure is intendedto cover any adaptations or variations of the exemplary embodiment(s).In addition, in this disclosure, the terms “comprise” or “comprising” donot exclude other elements or steps, the terms “a” or “one” do notexclude a plural number, and the term “or” means either or both.Furthermore, characteristics or steps which have been described may alsobe used in combination with other characteristics or steps and in anyorder unless the disclosure or context suggests otherwise. Thisdisclosure hereby incorporates by reference the complete disclosure ofany patent or application from which it claims benefit or priority.

1. A wing for an aircraft, comprising a main wing, and a leading edgehigh lift assembly comprising a high lift body, and a connectionassembly connecting the high lift body to the main wing in such a waythat the high lift body is movable relative to the main wing between astowed position and a deployed position, wherein the connection assemblycomprises at least one rotation element that is mounted to the high liftbody and that is mounted to the main wing rotatably about an axis ofrotation, wherein the main wing comprises an upper skin panel and alower skin panel, wherein the upper skin panel has a leading edgeportion, wherein the high lift body extends between a leading edge and atrailing edge, wherein the trailing edge of the high lift body isconfigured to move along the leading edge portion of the upper skinpanel of the main wing, when the high lift body is moved between thestowed position and the deployed position, wherein the leading edgeportion of the upper skin panel is configured to be elastically deformedwhen the high lift body is moved from the stowed position to thedeployed position.
 2. The wing according to claim 1, wherein the leadingedge portion of the upper skin panel is configured to be elasticallydeformed, when the high lift body is moved from the stowed position tothe deployed position, by at least one link element rotatably mounted tothe rotation element and rotatably mounted to the leading edge portionof the upper skin panel.
 3. The wing according to claim 1, wherein theleading edge portion of the upper skin panel is configured to beelastically deformed, when the high lift body is moved from the stowedposition to the deployed position, by at least one rope element attachedto the rotation element and attached to the leading edge portion of theupper skin panel.
 4. The wing according to claim 1, wherein the leadingedge portion of the upper skin panel is configured to be elasticallydeformed by the trailing edge of the high lift body moving along andcontacting the leading edge portion of the upper skin panel, when thehigh lift body is moved from the stowed position to the deployedposition.
 5. The wing according to claim 1, wherein the wing comprises arotary actuator for driving the rotation element about the axis ofrotation.
 6. The wing according to claim 5, wherein the rotary actuatoris mounted to the main wing and has a rotating drive arm linked to therotation element by a drive link that is rotatably mounted to the drivearm and that is rotatably mounted to the rotation element.
 7. The wingaccording to claim 5, wherein the rotary actuator comprises a firstrotating aim and a second rotating arm rotating in opposite directionsabout a common axis, wherein the first rotating arm is rotatably mountedto the main wing, and wherein the second rotating arm is rotatablymounted to the rotation element or to the high lift body.
 8. The wingaccording to claim 1, wherein at least one stiffener is provided at theleading edge portion of the upper skin panel, wherein the stiffenerextends in a span direction.
 9. The wing according to claim 8, whereinthe stiffener is formed separately from the upper skin panel and isattached to an inner surface of the leading edge portion of the upperskin panel.
 10. The wing according to claim 8, wherein the stiffener isformed integral with the leading edge portion of the upper skin panel.11. The wing according to claim 2, wherein at least one stiffener isprovided at the leading edge portion of the upper skin panel, whereinthe stiffener extends in a span direction, and wherein at least one ofthe link element or the rope element is attached to the leading edgeportion of the upper skin panel via the stiffener.
 12. The wingaccording to claim 8, wherein an extension of the stiffener normal tothe upper skin panel varies in the span direction.
 13. The wingaccording to claim 2, wherein at least one stiffener is provided at theleading edge portion of the upper skin panel, wherein the stiffenerextends in a span direction, wherein an extension of the stiffenernormal to the upper skin panel varies in the span direction, and whereinthe extension of the stiffener normal to the upper skin panel varies inthe span direction in such a way that a maximum extension is in an areaof an attachment of at least one of the link element or the ropeelement, while the extension is decreasing in the span direction withincreasing distance from the area of the attachment of at least one ofthe link element or the rope element.
 14. The wing according to claim 1,wherein the leading edge portion of the upper skin panel has a thicknessvarying in a chord direction.
 15. The wing according to claim 14,wherein the thickness of the leading edge portion of the upper skinpanel increases linearly in the chord direction downstream.
 16. The wingaccording to claim 1, wherein the leading edge portion of the upper skinpanel is made of a fiber reinforced plastic having a varying laminatelay-up in a chord direction.
 17. The wing according to claim 1, whereinthe leading edge portion of the upper skin panel is provided with atleast one reinforcement element extending in a chord direction to vary abending stiffness of the leading edge portion of the upper skin panelalong the chord direction.
 18. The wing according to claim 1, whereinthe leading edge high lift assembly comprises a further connectionassembly spaced from the connection assembly in a span direction.
 19. Aleading edge high lift assembly for the wing according to claim 1,comprising a high lift body, and a connection assembly configured toconnect the high lift body to a main wing such that the high lift bodyis movable relative to the main wing between a stowed position and adeployed position, wherein the connection assembly comprises a rotationelement that is mounted to the high lift body and that is configured tobe mounted to the main wing rotatably about an axis of rotation, whereinthe high lift body extends between a leading edge and a trailing edge,wherein, in an installed state, the trailing edge of the high lift bodyis configured to move along the leading edge portion of an upper skinpanel of the main wing, when the high lift body is moved between thestowed position and the deployed position, wherein the leading edge highlift assembly is configured such that in an installed state the leadingedge portion of the upper skin panel can be elastically deformed, whenthe high lift body is moved from the stowed position to the deployedposition.
 20. An aircraft comprising the wing according to claim 1.